@Article{DomingosPradMora:2013:StSiDo,
               author = "Domingos, R. C. and Prado, Antonio Fernando Bertachini de Almeida 
                         and Moraes, R. Villhena de",
          affiliation = "Instituto Nacional de Pesquisas Espaciais (INPE), 12227-010 
                         S{\~a}o Jos{\'e} dos Campos, SP, Brazil and {Instituto Nacional 
                         de Pesquisas Espaciais (INPE)} and Universidade Federal de 
                         S{\~a}o Paulo (UNIFESP), 12231-280 S{\~a}o Jos{\'e} dos Campos, 
                         SP, Brazil",
                title = "A study of single- and double-averaged second-order models to 
                         evaluate third-body perturbation considering elliptic orbits for 
                         the perturbing body",
              journal = "Mathematical Problems in Engineering",
                 year = "2013",
               volume = "2013",
               number = "ID260830",
             keywords = "Critical angles, Disturbing function, Elliptic orbit, Initial 
                         eccentricity, Legendre polynomials, Restricted three-body problem, 
                         Second-order models, Third-body perturbations, Astronomy, 
                         Equations of motion, Orbits, Spacecraft.",
             abstract = "The equations for the variations of the Keplerian elements of the 
                         orbit of a spacecraft perturbed by a third body are developed 
                         using a single average over the motion of the spacecraft, 
                         considering an elliptic orbit for the disturbing body. A 
                         comparison is made between this approach and the more used double 
                         averaged technique, as well as with the full elliptic restricted 
                         three-body problem. The disturbing function is expanded in 
                         Legendre polynomials up to the second order in both cases. The 
                         equations of motion are obtained from the planetary equations, and 
                         several numerical simulations are made to show the evolution of 
                         the orbit of the spacecraft. Some characteristics known from the 
                         circular perturbing body are studied: circular, elliptic 
                         equatorial, and frozen orbits. Different initial eccentricities 
                         for the perturbed body are considered, since the effect of this 
                         variable is one of the goals of the present study. The results 
                         show the impact of this parameter as well as the differences 
                         between both models compared to the full elliptic restricted 
                         three-body problem. Regions below, near, and above the critical 
                         angle of the third-body perturbation are considered, as well as 
                         different altitudes for the orbit of the spacecraft. © 2013 R. C. 
                         Domingos et al.",
                  doi = "10.1155/2013/260830",
                  url = "http://dx.doi.org/10.1155/2013/260830",
                 issn = "1024-123X",
                label = "scopus 2013-11",
             language = "en",
        urlaccessdate = "20 maio 2024"
}